U.S. patent number 10,794,284 [Application Number 16/501,582] was granted by the patent office on 2020-10-06 for seal plate with fluid bypass control.
This patent grant is currently assigned to RAYTHEON TECHNOLOGIES CORPORATION. The grantee listed for this patent is UNITED TECHNOLOGIES CORPORATION. Invention is credited to Jonas S. Banhos, William Meyst, Andre Herman Troughton.
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United States Patent |
10,794,284 |
Meyst , et al. |
October 6, 2020 |
Seal plate with fluid bypass control
Abstract
The present disclosure relates generally to a manifold including
a plurality of manifold channels disposed therethrough, each
manifold channel including a manifold channel opening, and a seal
plate, including a plurality of seal plate apertures disposed
thereon, operably coupled to the manifold, wherein the seal plate
includes at least one seal plate channel extending between at least
two of the plurality of seal plate apertures.
Inventors: |
Meyst; William (Middletown,
CT), Banhos; Jonas S. (New York, NY), Troughton; Andre
Herman (Windsor Locks, CT) |
Applicant: |
Name |
City |
State |
Country |
Type |
UNITED TECHNOLOGIES CORPORATION |
Farmington |
CT |
US |
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Assignee: |
RAYTHEON TECHNOLOGIES
CORPORATION (Farmington, CT)
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Family
ID: |
1000005096380 |
Appl.
No.: |
16/501,582 |
Filed: |
May 6, 2019 |
Prior Publication Data
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Document
Identifier |
Publication Date |
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US 20190264611 A1 |
Aug 29, 2019 |
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Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
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14623309 |
Feb 16, 2015 |
10280840 |
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61980090 |
Apr 16, 2014 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F02C
7/28 (20130101); F01D 25/183 (20130101); F02C
7/06 (20130101); F01D 25/18 (20130101); F05D
2240/55 (20130101); F05D 2260/98 (20130101); F05D
2220/32 (20130101) |
Current International
Class: |
F02C
7/06 (20060101); F01D 25/18 (20060101); F02C
7/28 (20060101) |
Field of
Search: |
;137/884 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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0540192 |
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May 1993 |
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EP |
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0540192 |
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May 1993 |
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EP |
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Other References
European Communication and Search Report; Application No.
15163830.1-1607; dated Sep. 9, 2015; 6 pages. imported from a
related application.
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Primary Examiner: Barry; Daphne M
Attorney, Agent or Firm: Cantor Colburn LLP
Parent Case Text
CROSS-REFERENCES TO RELATED APPLICATIONS
The present application is a continuation of U.S. patent
application Ser. No. 14/623,309, filed Feb. 16, 2015 and published
Dec. 8, 2016 as US 2016/0356220 which claims the benefit of U.S.
Provisional Patent Application No. 61/980,090, filed Apr. 16, 2014,
all of which are hereby incorporated by reference in their
entireties.
Claims
What is claimed is:
1. A manifold assembly comprising: a first manifold including a
plurality of exterior surfaces including a manifold top surface; a
first manifold channel and a second manifold channel, each
extending between the manifold top surface and another of the
plurality of exterior manifold surfaces; the first manifold channel
and the second manifold channel having a respective first channel
opening and second channel opening in the manifold top surface; a
seal plate having a seal plate top surface and a seal plate bottom
surface spaced from the seal plate top surface in a first
direction, the first direction being an axial direction that
defines a seal plate thickness; the seal plate bottom surface
disposed against the manifold top surface; a first seal plate
aperture and a second seal plate aperture extending through the
seal plate in the axial direction; the first seal plate aperture
and the second seal plate aperture respectively aligned with the
first channel opening and the second channel opening; a seal plate
channel extending in a second direction connecting the first seal
plate aperture and the second seal plate aperture, wherein the
second direction is perpendicular to the first direction; the seal
plate channel defining a fluid circuit between the first manifold
channel and the second manifold channel; and the seal plate channel
narrowing in a third direction, whereby the seal plate channel is
configured to control a flow characteristic of the fluid circuit,
and wherein the third direction is perpendicular to the first
direction and the second direction.
2. The seal plate of claim 1, wherein the flow characteristic
configured to be controlled by the seal plate channel is one or
more of flow pressure drop, flow temperature and mass flow
rate.
3. The assembly of claim 1, comprising: a first conduit and a
second conduit comprising respective first and second conduit ends;
and the first and second conduit ends respectively connecting to
the top surface of the seal plate and being aligned with the first
seal plate aperture and the second seal plate aperture.
4. The assembly of claim 3, wherein: the first conduit and second
conduit comprise respective third and fourth conduit ends that are
configured for connecting to a second manifold.
5. A gas turbine engine comprising the assembly of claim 4.
6. The assembly of claim 1, wherein the seal plate channel
comprises a venturi type channel.
7. The assembly of claim 1, wherein: the seal plate channel defines
a restriction in the third direction; the restriction is located in
the middle, in the second direction, of the seal plate channel; and
the restriction widens in the third direction proximate the first
seal plate aperture and the second seal plate aperture.
8. The assembly of claim 1, wherein the seal plate channel defines
a geometric step-wise restriction in the third direction.
Description
TECHNICAL FIELD OF THE DISCLOSED EMBODIMENTS
The present disclosure is generally related to gas turbine engines
and, more specifically, to a seal plate with fluid bypass
control.
BACKGROUND OF THE DISCLOSED EMBODIMENTS
Traditionally, manifolds for use with gas turbine engines are
comprised of a single-piece part that comprises a cast component
with cored flow passages. As fluids are pumped through the
manifold, pressure builds therein which requires a bypass to
relieve the pressure. Such bypasses may be integral to the manifold
or external; thus, resulting in increased costs for the manifold
assembly.
Improvements in manifold assemblies are therefore needed in the
art.
SUMMARY OF THE DISCLOSED EMBODIMENTS
In one aspect, a manifold assembly is provided. The manifold
assembly includes a manifold including a plurality of manifold
channels disposed therethrough, each of the plurality of manifold
channels including a manifold channel opening. The manifold
assembly further includes a seal plate operably coupled to the
manifold. The seal plate includes a, plurality of seal plate
apertures disposed thereon. Each of the manifold channel openings
are aligned with a respective one of the seal plate apertures.
The seal plate further includes at least one seal plate channel
connecting at least two of the plurality of seal plate apertures to
allow a fluid to pass therethrough. In at least one embodiment, the
at least two seal plate apertures connected by the at least one
seal plate channel are adjacent to one another.
In at least one embodiment, the at least one seal plate channel
includes a bypass type channel. In at least one embodiment, the at
least one seal plate channel includes a venturi type channel. In at
least one embodiment, the at least one seal plate channel includes
an orifice type channel. In at least one embodiment, a first one of
the at least one seal plate channels extends between a first one of
the plurality of seal plate apertures and a second one of the at
least one seal plate channels.
Other embodiments are also disclosed.
BRIEF DESCRIPTION OF THE DRAWINGS
The embodiments and other features, advantages and disclosures
contained herein, and the manner of attaining them, will become
apparent and the present disclosure will be better understood by
reference to the following description of various exemplary
embodiments of the present disclosure taken in conjunction with the
accompanying drawings, wherein:
FIG. 1 is a schematic cross-sectional view of a gas turbine
engine;
FIG. 2 is a perspective view of a manifold assembly in an
embodiment;
FIG. 3 is a cross-sectional view of a manifold assembly in an
embodiment;
FIGS. 4A-D are front views of embodiments of seal plate channels;
and
FIG. 5 is a perspective view of a pair of manifold assemblies
operably coupled to one another to create a fluid circuit in an
embodiment.
DETAILED DESCRIPTION OF THE DISCLOSED EMBODIMENTS
For the purposes of promoting an understanding of the principles of
the present disclosure, reference will now be made to the
embodiments illustrated in the drawings, and specific language will
be used to describe the same. It will nevertheless be understood
that no limitation of the scope of this disclosure is thereby
intended.
FIG. 1 schematically illustrates a gas turbine engine 20. The gas
turbine engine 20 is disclosed herein as a two-spool turbofan that
generally incorporates a fan section 22, a compressor section 24, a
combustor section 26 and a turbine section 28. Alternative engines
might include an augmentor section (not shown) among other systems
or features. The fan section 22 drives air along a bypass flow path
B in a bypass duct, while the compressor section 24 drives air
along a core flow path C for compression and communication into the
combustor section 26 then expansion through the turbine section 28.
Although depicted as a two-spool turbofan gas turbine engine in the
disclosed non-limiting embodiment, it should be understood that the
concepts described herein are not limited to use with two-spool
turbofans as the teachings may be applied to other types of turbine
engines including three-spool architectures.
The exemplary engine 20 generally includes a low speed spool 30 and
a high speed spool 32 mounted for rotation about an engine central
longitudinal axis A relative to an engine static structure 36 via
several bearing systems 38. It should be understood that various
bearing systems 38 at various locations may alternatively or
additionally be provided, and the location of bearing systems 38
may be varied as appropriate to the application.
The low speed spool 30 generally includes an inner shaft 40 that
interconnects a fan 42, a low pressure compressor 44 and a low
pressure turbine 46. The inner shaft 40 is connected to the fan 42
through a speed change mechanism, which in exemplary gas turbine
engine 20 is illustrated as a geared architecture 48 to drive the
fan 42 at a lower speed than the low speed spool 30. The high speed
spool 32 includes an outer shaft 50 that interconnects a high
pressure compressor 52 and high pressure turbine 54. A combustor 56
is arranged in exemplary gas turbine 20 between the high pressure
compressor 52 and the high pressure turbine 54. An engine static
structure 36 is arranged generally between the high pressure
turbine 54 and the low pressure turbine 46. The engine static
structure 36 further supports bearing systems 38 in the turbine
section 28. The inner shaft 40 and the outer shaft 50 are
concentric and rotate via bearing systems 38 about the engine
central longitudinal axis A which is collinear with their
longitudinal axes.
The core airflow is compressed by the low pressure compressor 44
then the high pressure compressor 52, mixed and burned with fuel in
the combustor 56, then expanded over the high pressure turbine 54
and low pressure turbine 46. The turbines 46, 54 rotationally drive
the respective low speed spool 30 and high speed spool 32 in
response to the expansion. It will be appreciated that each of the
positions of the fan section 22, compressor section 24, combustor
section 26, turbine section 28, and fan drive gear system 48 may be
varied. For example, gear system 48 may be located aft of combustor
section 26 or even aft of turbine section 28, and fan section 22
may be positioned forward or aft of the location of gear system
48.
The engine 20 in one example is a high-bypass geared aircraft
engine. In a further example, the engine 20 bypass ratio is greater
than about six (6), with an example embodiment being greater than
about ten (10), the geared architecture 48 is an epicyclic gear
train, such as a planetary gear system or other gear system, with a
gear reduction ratio of greater than about 2.3 and the low pressure
turbine 46 has a pressure ratio that is greater than about five. In
one disclosed embodiment, the engine 20 bypass ratio is greater
than about ten (10:1), the fan diameter is significantly larger
than that of the low pressure compressor 44, and the low pressure
turbine 46 has a pressure ratio that is greater than about five
5:1. Low pressure turbine 46 pressure ratio is pressure measured
prior to inlet of low pressure turbine 46 as related to the
pressure at the outlet of the low pressure turbine 46 prior to an
exhaust nozzle. The geared architecture 48 may be an epicycle gear
train, such as a planetary gear system or other gear system, with a
gear reduction ratio of greater than about 2.3:1. It should be
understood, however, that the above parameters are only exemplary
of one embodiment of a geared architecture engine and that the
present invention is applicable to other gas turbine engines
including direct drive turbofans.
A significant amount of thrust is provided by the bypass flow B due
to the high bypass ratio. The fan section 22 of the engine 20 is
designed for a particular flight condition--typically cruise at
about 0.8 Mach and about 35,000 feet (10,688 meters). The flight
condition of 0.8 Mach and 35,000 ft., with the engine at its best
fuel consumption--also known as "bucket cruise Thrust Specific Fuel
Consumption (`TSFC`)" --is the industry standard parameter of lbm
of fuel being burned divided by lbf of thrust the engine produces
at that minimum point. "Low fan pressure ratio" is the pressure
ratio across the fan blade alone, without a Fan Exit Guide Vane
("FEGV") system. The low fan pressure ratio as disclosed herein
according to one non-limiting embodiment is less than about 1.45.
"Low corrected fan tip speed" is the actual fan tip speed in ft/sec
divided by an industry standard temperature correction of [(Tram
.degree. R)/(518.7.degree. R)].sup.0.5. The "Low corrected fan tip
speed" as disclosed herein according to one non-limiting embodiment
is less than about 1150 ft/second (350.5 m/sec).
FIGS. 2 and 3 schematically illustrate a manifold assembly 60. The
manifold assembly 60 includes a manifold 62 having a manifold first
surface 63A (FIG. 3) which is a top surface of the manifold and a
manifold second surface 63B (FIG. 5) which is a bottom surface of
the manifold, and including a plurality of manifold channels 64
(channels 64A and 64B shown) disposed therethrough, each of the
plurality of manifold channels 64 including a manifold channel
opening 66. The manifold assembly 60 further includes a seal plate
68, with a seal plate top surface 68A and a seal plate bottom
surface 68B, operably coupled to the manifold 62. It will be
appreciated that the seal plate may be composed of any suitable
material such as aluminum, steel, and titanium to name a few
non-limiting examples. The seal plate 68 includes a plurality of
seal plate apertures 70 disposed thereon. Each of the manifold
channel openings 66 are aligned with a respective one of the seal
plate apertures 70.
The seal plate 68 further includes at least one seal plate channel
72 connecting at least two of the plurality of seal plate apertures
70 to allow a fluid to pass therethrough. In at least one
embodiment, the at least two seal plate apertures 70 connected by
the at least one seal plate channel 72 are adjacent to one another.
The at least one seal plate channel 72 is configured to regulate a
fluid pressure of a fluid circuit later described herein.
In at least one embodiment, as shown in FIG. 4A, the at least one
seal plate channel 72 includes a bypass type channel. In at least
one embodiment, as shown in FIG. 48, the at least one seal plate
channel 72 includes a venturi type channel. As defined herein, a
venturi type channel is an opening which employs a temporary
restriction or narrowing along at least a portion of its length. In
at least one embodiment, as shown in FIG. 4C, the at least one seal
plate channel 72 includes an orifice type channel. As defined
herein, an orifice type channel is an opening which employs a
temporary restriction in the middle and widens towards the ends.
FIG. 4D shows an embodiment where a first seal plate channel 72A
extends between seal plate apertures 70A and 708, positioned
adjacent to one another, and a second seal plate channel 728
extending between seal plate aperture 70C and the first seal plate
channel 72A. This arrangement may be used to reduce fluid pressure
within a fluid circuit connected to seal plate apertures 70A and
708, as well as expel fluid from the manifold 62 through seal plate
aperture 70C. Generally, the arrangements of FIGS. 4A-4D may be
used to control, such as fine tune and/or reduce, pressure drop
within the fluid circuit, to provide a bypass to the fluid circuit
for example to control temperature within the fluid circuit,
and/or, in the case of the venturi type channel 72, to control mass
flow through the fluid circuit.
FIG. 5 schematically illustrates a seal plate 68 operably coupled
to a first manifold assembly 60, and a second manifold assembly
(not shown) operably coupled to the seal plate 68 via a pair of
conduits 76 and 78. The conduits 76 and 78 create a fluid circuit
to circulate a fluid between the first manifold assembly 60 and the
second manifold assembly at a circuit flow rate. For example, oil
to name one non-limiting example, is circulated between the
manifold channel 64A (as shown in FIG. 3) of the first manifold
assembly 60 through conduit 76 to a manifold channel (not shown) of
the second manifold assembly. The fluid returns to the manifold
channel 64B of first manifold assembly 60 via the conduit 78. Fluid
is circulated in the aforementioned fluid circuit to aid in the
lubrication of parts within the gas turbine engine 20. As the fluid
circulates between the first manifold assembly 60 and the second
manifold assembly, pressure builds within the fluid circuit. To
relieve and/or regulate the fluid pressure within the fluid
circuit, the at least one seal plate channel 72 creates a bypass
between manifold channels 64A and 64B. It will be appreciated that
the geometry of the at least one seal plate channel 72 and the
cross-sectional area of the at least one seal plate channel 72 is
selected based on a mass flow rate and a downstream pressure drop
of the fluid circuit.
It will be appreciated that the seal plate 68 includes at least one
seal plate channel 72 connecting at least two of the plurality of
seal plate apertures 70 disposed thereon to create a bypass that
regulates the pressure in a fluid circuit. It will also be
appreciated that the at least one seal plate channel 72 reduces
costs of the manifold assembly 60, and increases design flexibility
of the manifold assembly 60 to meet flow requirements of the fluid
circuit as additional parts or machine tooling would not be
required to create a necessary bypass.
While the invention has been illustrated and described in detail in
the drawings and foregoing description, the same is to be
considered as illustrative and not restrictive in character, it
being understood that only certain embodiments have been shown and
described and that all changes and modifications that come within
the spirit of the invention are desired to be protected.
* * * * *